Ring gear mounting arrangement with oil scavenge scheme

Abstract

An epicyclic gear train for a turbine engine includes a gutter with an annular channel. A rotating structure includes a ring gear that has an aperture that is axially aligned with the annular channel. Axially spaced apart walls extend radially outward relative to the rotating structure to define a passageway. The passageway is arranged radially between and axially aligned with the aperture and the annular channel. The walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel.

What is claimed is: 
     
       1. An epicyclic gear train for a turbine engine comprising:
 a gutter with an annular channel; 
 a rotating structure includes a ring gear, the rotating structure has an aperture that is axially aligned with the annular channel; and 
 axially spaced apart walls that extend radially outward relative to the rotating structure to define a passageway, the passageway is arranged radially between and axially aligned with the aperture and the annular channel, wherein the walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel. 
 
     
     
       2. The epicyclic gear train according to  claim 1 , comprising a fixed structure that supports the gutter. 
     
     
       3. The epicyclic gear train according to  claim 1 , wherein the walls are supported by the rotating structure. 
     
     
       4. The epicyclic gear train according to  claim 1 , wherein the gutter has a U-shaped cross-section. 
     
     
       5. The epicyclic gear train according to  claim 1 , wherein the walls each include a face that together define the passageway. 
     
     
       6. The epicyclic gear train according to  claim 1 , wherein the walls are arranged radially inward from the gutter. 
     
     
       7. The epicyclic gear train according to  claim 1 , wherein the ring gear includes holes extending therethrough that provide the aperture. 
     
     
       8. The epicyclic gear train according to  claim 1 , comprising a seal arranged on each of axially opposing sides of the ring gear, the seals providing the walls. 
     
     
       9. The epicyclic gear train according to  claim 8 , wherein each seal includes a radially outwardly extending knife edge seal, the knife edge seals configured to further inhibit the axial flow of the oil passing from the aperture toward the annular channel. 
     
     
       10. The epicyclic gear train according to  claim 1 , wherein the rotating structure is configured to rotate about an axis extending in an axial direction, the axial flow configured to flow in the axial direction. 
     
     
       11. The epicyclic gear train according to  claim 10 , wherein the rotating structure includes a sun gear coaxial with the axis, and multiple star gears arranged circumferentially about and meshing with the sun gear, and the ring gear is arranged about and intermeshes with the star gears. 
     
     
       12. The epicyclic gear train according to  claim 11 , wherein the ring gear includes first and second portions operatively secured to one another by fastening elements. 
     
     
       13. The epicyclic gear train according to  claim 11 , wherein the rotating structure has a carrier that is operatively connected to a fixed structure, the carrier rotationally supports the star gears. 
     
     
       14. The epicyclic gear train according to  claim 11 , wherein the ring gear is operatively affixed to a shaft. 
     
     
       15. The epicyclic gear train according to  claim 14 , wherein a fan section is operatively connected to the shaft. 
     
     
       16. A gas turbine engine comprising:
 a fan section; 
 a turbine section; 
 an epicyclic gear train interconnecting the fan section and the turbine section, the epicyclic gear train including:
 a gutter with an annular channel; 
 a rotating structure includes a ring gear, the rotating structure has an aperture that is axially aligned with the annular channel; and 
 axially spaced apart walls that extend radially outward relative to the rotating structure to define a passageway, the passageway is arranged radially between and axially aligned with the aperture and the annular channel, wherein the walls are configured to inhibit an axial flow of an oil passing from the aperture toward the annular channel. 
 
 
     
     
       17. The gas turbine engine according to  claim 16 , comprising a fixed structure that supports the gutter. 
     
     
       18. The gas turbine engine according to  claim 16 , wherein the walls are supported by the rotating structure. 
     
     
       19. The gas turbine engine according to  claim 16 , wherein the gutter has a U-shaped cross-section. 
     
     
       20. The gas turbine engine according to  claim 16 , wherein the walls each include a face that together define the passageway. 
     
     
       21. The gas turbine engine according to  claim 16 , wherein the walls are arranged radially inward from the gutter. 
     
     
       22. The gas turbine engine according to  claim 16 , wherein the ring gear includes holes extending therethrough that provide the aperture. 
     
     
       23. The gas turbine engine according to  claim 16 , comprising a seal arranged on each of axially opposing sides of the ring gear, the seals providing the walls. 
     
     
       24. The gas turbine engine according to  claim 23 , wherein each seal includes a radially outwardly extending knife edge seal, the knife edge seals configured to further inhibit the axial flow of the oil passing from the aperture toward the annular channel. 
     
     
       25. The gas turbine engine according to  claim 16 , wherein the rotating structure is configured to rotate about an axis extending in an axial direction, the axial flow configured to flow in the axial direction. 
     
     
       26. The gas turbine engine according to  claim 25 , wherein the rotating structure includes a sun gear coaxial with the axis, and multiple star gears arranged circumferentially about and meshing with the sun gear, and the ring gear is arranged about and intermeshes with the star gears. 
     
     
       27. The gas turbine engine according to  claim 26 , wherein the ring gear includes first and second portions operatively secured to one another by fastening elements. 
     
     
       28. The gas turbine engine according to  claim 26 , wherein the rotating structure has a carrier that is operatively connected to a fixed structure, the carrier rotationally supports the star gears. 
     
     
       29. The gas turbine engine according to  claim 26 , wherein the ring gear is operatively affixed to a shaft. 
     
     
       30. The gas turbine engine according to  claim 29 , wherein the fan section is operatively connected to the shaft.